CN111365145B - Reusable igniter for rocket engine - Google Patents
Reusable igniter for rocket engine Download PDFInfo
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- CN111365145B CN111365145B CN202010254465.5A CN202010254465A CN111365145B CN 111365145 B CN111365145 B CN 111365145B CN 202010254465 A CN202010254465 A CN 202010254465A CN 111365145 B CN111365145 B CN 111365145B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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Abstract
The invention discloses a reusable igniter for rocket engines, comprising: the electric control solid propellant powder burning device comprises an outer electrode and an inner electrode, wherein a burning cavity for containing the electric control solid propellant is arranged between the outer electrode and the inner electrode; the outer electrode surrounds the periphery of the combustion cavity, and the inner electrode is inserted into the electric control solid propellant; the conductive assembly comprises an outer electrode conductive assembly and an inner electrode conductive assembly which are electrically connected with the outer electrode and the inner electrode; the outer electrode is provided with a nozzle communicated with the combustion cavity; the combustion cavity is provided with a communicating cavity near the nozzle end, the communicating cavity is not filled with the electric control solid propellant, and the gas generated after the electric control solid propellant is ignited flows to the nozzle. The igniter provided by the invention can realize multiple times of ignition, can be repeatedly used and has controllable ignition intensity.
Description
Technical Field
The invention relates to the technical field of ignition starting of engines, in particular to a reusable igniter for a rocket engine.
Background
The liquid ram rocket engine adopts liquid fuel and has the advantages of high speed, high maneuvering trajectory, long range and the like. The electric control solid propellant generally adopts an oxidant and a bonding agent with high oxygen content, has the advantages of repeatable ignition, controllable burning rate, good environmental performance, safety, good economy and the like, and can be widely applied to the commercial or military field.
The ignition device is one of the key components of a liquid ramjet rocket engine and functions to accurately and reliably ignite fuel, establish it and perform stable combustion. However, organization of stable combustion in a high velocity gas stream requires that the injection, atomization, fuel-air mixing, and combustion reactions of the fuel be completed in a short time, and thus sufficient ignition energy be necessary to ignite the combustible mixture. For liquid ramjet engines using liquid hydrocarbon as fuel, it is necessary to undergo droplet breaking, atomization, evaporation and mixing, resulting in a total ignition delay time of the fuel much longer than its residence time in the combustion chamber, and thus it is difficult to achieve ignition, flame propagation, flame maintenance and stable combustion of the fuel in the combustion chamber under a limited length of high-velocity gas flow.
At present, the ignition mode which is commonly used for the liquid ram rocket engine mainly comprises the following steps: the jet ignition is realized by injecting high-energy airflow into the combustion chamber, the ignition system and the combustion chamber are relatively independent in structure, the intensity of ignition energy, the ignition position, the action mode and the like are easy to control and adjust, but the ignition can not be carried out for many times, and the igniter is easy to quench due to large liquid fuel flow, so that the combustion is unstable. In addition, the more commonly used ignition modes comprise pyrotechnic agent ignition, self-ignition, torch-type ignition, laser ignition and the like, wherein the pyrotechnic agent ignition mode is developed more mature and has the advantages of simple structure, high combustion product temperature and the like, but the ignition mode can not be ignited for many times, has high ignition danger, long installation preparation time of an ignition device and the like, and influences the ignition reliability and stability of the liquid ram rocket engine.
Disclosure of Invention
The invention provides a reusable igniter for a rocket engine, which is used for overcoming the defects that the ignition and combustion of a liquid ram rocket engine are unstable and the repeated ignition can not be carried out for many times in the prior art.
To achieve the above object, the present invention proposes a reusable igniter for a rocket engine, comprising:
the electric control solid propellant powder burning device comprises an outer electrode and an inner electrode, wherein a burning cavity for containing the electric control solid propellant is arranged between the outer electrode and the inner electrode;
the outer electrode surrounds the periphery of the combustion cavity, and the inner electrode is inserted into the electric control solid propellant;
the conductive assembly comprises an outer electrode conductive assembly and an inner electrode conductive assembly which are electrically connected with the outer electrode and the inner electrode;
the outer electrode is provided with a nozzle communicated with the combustion cavity;
the combustion cavity is provided with a communicating cavity near the nozzle end, the communicating cavity is not filled with the electric control solid propellant, and the gas generated after the electric control solid propellant is ignited flows to the nozzle.
Compared with the prior art, the invention has the beneficial effects that:
1. the reusable igniter for the rocket engine provided by the invention has the advantages that the outer electrode and the inner electrode are simultaneously electrified through the conductive assembly, the ignition of the electric control solid propellant is realized, the ignition of the rocket engine is realized, the ignition can be realized by electrifying, and the time required by ignition is short; and the igniter stops working after the electrification is stopped. Therefore, the igniter provided by the invention can realize multiple times of ignition and can be repeatedly used.
2. According to the reusable igniter for the rocket engine, the combustion cavity is arranged in the igniter, and the electrically-controlled solid propellant is filled in the combustion cavity, so that the phenomenon that the igniter is easy to quench due to large liquid fuel flow in the prior art can be effectively avoided.
3. The reusable igniter for the rocket engine provided by the invention can regulate and control the burning speed of the electric control solid propellant by changing the input voltage, thereby controlling the ignition intensity.
4. The reusable igniter for the rocket engine provided by the invention has a simple structure, is relatively independent from a combustion chamber structure, and is convenient to control and adjust the ignition position.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a block diagram of a reusable igniter for a rocket engine as provided in example 1;
FIG. 2a is a block diagram of the electrically conductive assembly of the reusable igniter for a rocket motor as provided in example 1;
FIG. 2b is a cross-sectional view of the electrically conductive assembly of the reusable igniter for a rocket motor provided in example 1;
FIG. 3a is a schematic diagram of the inner electrode structure of the reusable igniter for rocket motors provided in example 1;
FIG. 3b is a cross-sectional view of the ceramic insulator of the reusable igniter for a rocket motor provided in example 1;
FIG. 4 is a structural view of a ground test stand of the liquid rocket engine in example 2;
FIG. 5 is a structure diagram of a ground test stand of the scramjet engine in example 3.
The reference numbers illustrate: 1-nozzle, 2-combustion chamber, 3-outer electrode, 4-inner electrode, 5-ceramic insulator, 6-wiring terminal, 7-electrode column, 8-insulating layer, 9-conductive disc, 10-conductive rod, 11-conductive elastic insert, 12-inner ring, 13-external thread interface, 14-elastic insulating seal ring, 15-power supply unit, 16-igniter, 17-insulating heat-insulating protective sleeve, 18-tail base, 19-engine external thread interface, 20-fixing sleeve and 21-engine cavity internal thread interface.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The invention provides a reusable igniter for a rocket engine, comprising:
the electric control solid propellant powder burning device comprises an outer electrode and an inner electrode, wherein a burning cavity for containing the electric control solid propellant is arranged between the outer electrode and the inner electrode;
the outer electrode surrounds the periphery of the combustion cavity, and the inner electrode is inserted into the electric control solid propellant;
the conductive assembly comprises an outer electrode conductive assembly and an inner electrode conductive assembly which are electrically connected with the outer electrode and the inner electrode;
the outer electrode is provided with a nozzle communicated with the combustion cavity;
the combustion cavity is provided with a communicating cavity near the nozzle end, the communicating cavity is not filled with the electric control solid propellant, and the gas generated after the electric control solid propellant is ignited flows to the nozzle.
The outer electrode conducting component is electrically connected with the outer electrode to enable the outer electrode to be positively charged;
the inner electrode conducting component is electrically connected with the inner electrode to enable the inner electrode to be charged with negative electricity.
Preferably, the electrically controlled solid propellant is a novel energetic material capable of releasing a large amount of gas when energized. The electric control solid propellant can be ignited immediately after the igniter is electrified, so that a large amount of gas is released by the electric control solid propellant, and the ignition is realized. The proper electrically controlled solid propellant is selected to ensure ignition stability.
Preferably, the conductive assembly comprises a terminal, one end of the terminal is arranged in a coaxial annular structure and comprises an inner ring and an outer ring;
the outer electrode conductive component is an external thread interface arranged on the outer ring and is used for being in threaded connection with the outer electrode; the external thread interface on the outer ring is made of a conductive material, and the other parts of the external thread interface are made of an insulating material;
the inner electrode conductive component is a conductive elastic insertion piece arranged in the inner ring and used for being inserted with the inner electrode; the inner ring is made of insulating materials.
The structure design of the inner ring and the outer ring of the wiring terminal is to isolate the positive pole and the negative pole of the circuit and avoid the short circuit of the circuit.
Preferably, the conductive assembly further comprises a power supply unit disposed at the other end of the connection terminal;
the power supply unit comprises two power supply layers and two insulating layers which are used for wrapping the power supply layers respectively;
the power supply unit is connected with an external power supply, and the external power supply supplies power to the external thread interface and the conductive elastic insertion piece respectively through two layers of power supply layers.
The external power source can be direct current, alternating current or pulse electricity to rapidly ignite the electrically controlled solid propellant.
The power supply unit has a simple structure, and is distributed at one end of the conductive component, so that the wiring on the outer wall surface of the engine can be avoided, the design complexity of the engine is reduced, and the safety performance of the engine is improved. In addition, the four-layer design of the power supply unit can effectively avoid the occurrence of short circuit of the two power supply layers.
Preferably, an elastic insulating sealing ring is arranged at the joint of the external thread interface and the external electrode, so that air leakage is prevented, and damage to the wiring terminal due to temperature rise of the external thread interface caused by electrification is prevented.
Preferably, the outer electrode and the inner electrode are fixedly connected through a ceramic insulating part;
the ceramic insulating part is positioned in the combustion cavity, and two ends of the ceramic insulating part are respectively embedded into the inner wall of the outer electrode;
the ceramic insulating part is provided with at least one through hole, and the inner electrode penetrates through the through hole and is inserted into the electric control solid propellant.
The outer electrode and the inner electrode are isolated by a ceramic insulator. Preferably, the ceramic insulator is made of alumina high-temperature resistant ceramic material to enhance the high-temperature resistance.
Preferably, the inner electrode comprises at least one electrode column, a conductive disc and a conductive rod;
one end of the electrode column is fixedly connected to one side of the conductive disc, and one end of the conductive rod is fixedly connected to the other side of the conductive disc;
the other end of the electrode column penetrates through the through hole and is inserted into the electric control solid propellant;
the other end of the conducting rod is inserted into the inner ring and is connected with the conductive elastic insertion piece in an inserting mode.
After the electrode is powered on, the conductive elastic inserting pieces conduct electricity to the conductive rods, the conductive rods conduct electricity to the conductive discs, and the conductive discs finally conduct electricity to the electrode columns.
The number of electrode posts can be designed according to actual ignition requirements to enhance the application range of the igniter.
The electrode column, the conductive disc and the conductive rod are all conductive, the conductive rod is connected with the inner electrode conductive assembly in an inserting mode, and the conductive rod can rapidly enable the whole inner electrode to be negatively charged through the electric conduction of the inner electrode conductive assembly.
Preferably, the side edges of the electrode column are coated with an insulating layer. When the filling amount of the electric control solid propellant in the combustion cavity can completely coat the whole electrode column, the side edge of the electrode column is completely coated with the insulating layer, and the far conductive disc end of the electrode column is contacted with the electric control solid propellant, so that the first ignition of an igniter can be realized; when the electric control solid propellant filling amount in the combustion cavity only completely covers the side edge of the electrode column, the end, close to the conductive disc, of the side edge of the electrode column is coated with the insulating layer, the end, far away from the conductive disc, of the electrode column is not coated with the insulating layer, the part of the electrode column which is not coated with the insulating layer is contacted with the electric control solid propellant, and the igniter can ignite for the first time.
Preferably, the insulating layer is made of high-temperature-resistant insulating materials and covers the side edge of the inner electrode, so that the side edges of the electric-control solid propellant and the inner electrode are isolated, the electric-control solid propellant is prevented from being separated from an igniter device when being integrally electrified and combusted, and the insulating layer can be gradually ablated from the contact end of the electric-control solid propellant and the inner electrode in multiple ignition processes, so that multiple ignition and combustion of the electric-control solid propellant are ensured.
Preferably, the number of the electrode posts is consistent with that of the through holes; and an assembly gap of 0.1-0.2 mm is arranged between the electrode column and the through hole.
The assembly clearance is that the diameter of through-hole is 0.1 ~ 0.2mm more than the diameter of electrode post.
An assembly gap is reserved between the electrode column and the through hole to prevent the electrode column from heating and expanding after being electrified to damage the igniter structure.
Too large a fit gap may result in gas leakage, too small a fit gap may be insufficient, and the igniter structure may be damaged by heat expansion after the electrode column is energized.
Preferably, the assembly gap is sealed by ceramic-metal adhesive glue to prevent air leakage and has the functions of expansion with heat and contraction with cold.
Preferably, the outer electrode and the inner electrode are made of metal or alloy with high temperature resistance and strong electric conductivity to increase the electric conductivity of the inner and outer motors, thereby effectively shortening the ignition time.
The igniter provided by the invention can be used for rocket engines such as liquid rocket engines, liquid ramjets, scramjets and the like, and has a wide application range.
Example 1
The present embodiment provides a reusable igniter for a rocket engine, as shown in fig. 1, comprising:
the solid propellant gas-liquid separator comprises an outer electrode 3 and an inner electrode 4, wherein a combustion cavity for containing an electric control solid propellant is arranged between the outer electrode 3 and the inner electrode 4; in this embodiment, the electrically-controlled solid propellant comprises lithium perchlorate, polyvinyl alcohol, metal aluminum powder, water, a plasticizer, and the like.
The outer electrode 3 surrounds the periphery of the combustion cavity, and the inner electrode 4 is inserted into the electric control solid propellant;
the conductive assembly comprises an outer electrode conductive assembly and an inner electrode conductive assembly which are electrically connected with the outer electrode 3 and the inner electrode 4;
as shown in fig. 1, 2a and 2b, the conductive assembly includes a terminal 6, and one end of the terminal 6 is set to be a coaxial ring structure, which includes an inner ring 12 and an outer ring; and a welding point of an external power supply circuit is arranged between the inner ring 12 and the outer ring.
The outer electrode conductive component is an external thread interface 13 arranged on the outer ring and is used for being in threaded connection with the outer electrode 3; the external thread interface 13 on the outer ring is made of a conductive material, and the other parts of the external thread interface are made of an insulating material;
the inner electrode conductive component is a conductive elastic insertion sheet 11 arranged in the inner ring 12 and used for being inserted into the inner electrode 4; the inner ring 12 is made of an insulating material.
The conductive assembly further comprises a power supply unit 15, and the power supply unit 15 is arranged at the other end of the wiring terminal 6;
the power supply unit 15 comprises two power supply layers and two insulating layers which are respectively used for wrapping the power supply layers;
the power supply unit 15 is connected with an external power supply, and the external power supply supplies power to the external thread interface 13 and the conductive elastic insertion piece 11 through two layers of power supply layers respectively.
And an elastic insulating sealing ring 14 is arranged at the joint of the external thread interface 13 and the external electrode 3.
The outer electrode 3 and the inner electrode 4 are fixedly connected through a ceramic insulating part 5;
the ceramic insulating part 5 is positioned in the combustion cavity 2, and two ends of the ceramic insulating part are respectively embedded into the inner wall of the outer electrode 3;
three through holes are formed in the ceramic insulating part 5, and the inner electrode 4 penetrates through the through holes and is inserted into the electric control solid propellant. A cross-sectional view of the ceramic insulator 5 is shown in fig. 3 b.
The inner electrode 4 is shown in fig. 3a and comprises three electrode columns 7, a conductive disc 9 and a conductive rod 10;
one end of the electrode column 7 is fixedly connected to one side of the conductive disc 9, and one end of the conductive rod 10 is fixedly connected to the other side of the conductive disc 9;
the other end of the electrode column 7 penetrates through the through hole and is inserted into the electric control solid propellant; an assembly gap of 0.15mm is arranged between the electrode column and the through hole, and the assembly gap is sealed by ceramic-metal adhesive glue;
the other end of the conducting rod 10 is inserted into the inner ring 12 and is inserted into the conductive elastic insertion piece 11;
after being powered on, the conductive elastic insert 11 conducts electricity to the conductive rod 10, the conductive rod 10 conducts electricity to the conductive disc 9, and the conductive disc 9 finally conducts electricity to the electrode column 7.
The outer electrode 3 is provided with a nozzle 1 communicated with the combustion cavity;
and a communicating cavity is arranged at the end of the combustion cavity, which is close to the nozzle 1, and the communicating cavity is not filled with the electric control solid propellant and is used for enabling gas generated after the electric control solid propellant is ignited to flow to the nozzle.
In this embodiment, as shown in fig. 1, the communicating cavity is disposed between the other end of the electrode column 7 and the nozzle 1; the electric control solid propellant is filled in the non-communicated cavity part in the combustion cavity, and three electrode columns 7 of the inner electrode 4 are inserted in the electric control solid propellant; the three electrode columns 7 are coated with insulating layers 8 at the side edges of the near conductive disc 9 ends, and are directly contacted with the electric control solid propellant without being coated with the insulating layers 8 at the side edges (about 1mm in length) of the far conductive disc 9 ends so as to realize initial ignition.
Example 2
The present embodiment applies the igniter 16 provided in embodiment 1 to a liquid rocket engine, as shown in fig. 4, including: the ignition device comprises an igniter 16, a power supply unit 15, an insulating and heat-insulating protective sleeve 17, a tail base 18 and an engine external thread interface 19.
The tail base 18 is made of stainless steel and is a sealed cylinder with an internal thread opening at one end and a concave circular hole at the other end.
The shell of the igniter 16 and the engine are both in a cylindrical configuration; wherein, the liquid rocket engine combustion chamber department welds the external screw thread interface 19 of stainless steel material, and afterbody base 18 one end is equipped with the internal thread structure of mutually supporting with engine external screw thread interface 19. The housing of the igniter 16 is surrounded by an insulating protective boot 17 and nests in a tail base 18. The power supply unit 15 is matched and positioned with the other end of the tail base 18, and the contact part is sealed by a sealing ring, so that the igniter and the liquid rocket engine are fixed and sealed.
In this embodiment, the igniter 16 is powered to ignite, so that the electrically controlled solid propellant in the igniter 16 is ignited and burned rapidly to generate high temperature flame and energy for igniting the liquid rocket engine. One end of the power supply unit 15 is connected with the inner electrode and the outer electrode of the igniter, the other end of the power supply unit is connected with the liquid rocket engine control system and used for transmitting an ignition signal of the liquid rocket engine control system to the inner electrode and the outer electrode, the electric control solid propellant is ignited through electric energy, the burning speed is continuously stabilized for a plurality of seconds, high-temperature burning flame is generated, and the liquid rocket engine can be rapidly and reliably ignited. While the igniter 16 may be re-ignited by re-activating the ignition signal, possibly due to a flame-out caused by non-uniform mixing of the gas. In addition, the ignition energy can be controlled by adjusting the voltage according to the difference of the fuel flow of the liquid rocket engine.
Example 3
The present embodiment applies the igniter 16 provided in embodiment 1 to a liquid ram rocket engine, as shown in fig. 5, including: the liquid ramjet ignition device comprises 2 igniters 16 symmetrically arranged on two sides of a liquid ramjet engine, a power supply unit 15, an insulating and heat-insulating protective sleeve 17, a fixing sleeve 20 and an engine cavity internal thread interface 21.
The fixed sleeve 20 is made of a stainless pipe and is arranged at the concave cavity opening of the liquid ramjet, one end of the fixed sleeve 20 is provided with an external thread matched with the internal thread interface 21 of the concave cavity of the liquid ramjet, and the end is also provided with a round hole which is superposed with the central line of the nozzle 1 of the igniter and has a diameter slightly larger than that of the nozzle 1; the other end is provided with an annular concave table, and a round hole slightly larger than the diameter of the power supply unit 15 is arranged at the concave table and used for sealing the igniter.
In this embodiment, the igniter 16 is encased entirely within a layer of insulating boot 17 and then mounted within the retaining sleeve 20. One end of the fixing sleeve 20 is connected with a female screw interface 21 of the cavity of the liquid ramjet engine. The power supply unit 15 is matched and positioned with the other end of the fixed sleeve 20, and a sealing ring is sealed on the concave table, so that the igniter and the liquid ramjet can be fixed and sealed.
In this embodiment, the igniter 16 is electrically energized to ignite, so that the electrically controlled solid propellant in the igniter 16 is ignited and burned rapidly, thereby generating high-temperature flame and energy for igniting the liquid ramjet engine. One end of the power supply unit 15 is connected with the inner electrode and the outer electrode of the igniter, the other end of the power supply unit is connected with the control system of the liquid ramjet engine, and the power supply unit is used for transmitting an ignition signal of the control system of the liquid ramjet engine to the inner electrode and the outer electrode, igniting the electric control solid propellant through electric energy and continuously stabilizing the burning speed for a plurality of seconds to generate high-temperature burning flame, so that the liquid ramjet engine can burn quickly and reliably when fuel gas and air are. Meanwhile, when the air-fuel ratio is large, the igniter can be ignited again by starting the ignition signal again, and the flameout caused by the difficulty in ignition is possible. In addition, the ignition energy can be controlled by adjusting the voltage according to the fuel flow of the liquid ramjet.
Example 4
The present embodiment applies the igniter 16 provided in embodiment 1 to a scramjet engine, including: the igniter comprises an igniter, a power supply unit, an insulating and heat-insulating protective sleeve, an igniter base, an insulating flange plate and an engine concave cavity opening.
In this embodiment, the igniter 16 is electrically energized to ignite, so that the electrically controlled solid propellant in the igniter 16 is ignited and burned rapidly, thereby generating high-temperature flame and energy for igniting the liquid ramjet engine. One end of the power supply unit 15 is connected with the inner electrode and the outer electrode of the igniter, the other end of the power supply unit is connected with the scramjet engine control system, an ignition signal of the scramjet engine control system is transmitted to the inner electrode and the outer electrode, the electric control solid propellant is ignited through electric energy, the burning speed is continuously stabilized for a plurality of seconds, high-temperature burning flame is generated, and the scramjet engine can be rapidly and reliably ignited. Meanwhile, when the flameout which is possibly easily caused by supersonic airflow is generated, the igniter can be ignited again by starting the ignition signal again. In addition, the ignition energy can be controlled by adjusting the voltage according to the difference of the fuel flow of the scramjet engine.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (9)
1. A reusable igniter for a rocket engine, comprising:
the electric control solid propellant powder burning device comprises an outer electrode and an inner electrode, wherein a burning cavity for containing the electric control solid propellant is arranged between the outer electrode and the inner electrode;
the outer electrode surrounds the periphery of the combustion cavity, and the inner electrode is inserted into the electric control solid propellant;
the conductive assembly comprises an outer electrode conductive assembly and an inner electrode conductive assembly which are electrically connected with the outer electrode and the inner electrode; the conductive assembly comprises a wiring terminal, one end of the wiring terminal is arranged to be of a coaxial annular structure and comprises an inner ring and an outer ring;
the outer electrode conductive component is an external thread interface arranged on the outer ring and is used for being in threaded connection with the outer electrode; the external thread interface on the outer ring is made of a conductive material, and the other parts of the external thread interface are made of an insulating material;
the inner electrode conductive component is a conductive elastic insertion piece arranged in the inner ring and used for being inserted with the inner electrode; the inner ring is made of insulating materials;
the outer electrode is provided with a nozzle communicated with the combustion cavity;
the combustion cavity is provided with a communicating cavity near the nozzle end, the communicating cavity is not filled with the electric control solid propellant, and the gas generated after the electric control solid propellant is ignited flows to the nozzle.
2. A reusable igniter for a rocket engine as recited in claim 1, wherein said electrical conducting assembly further comprises a power supply unit, said power supply unit being disposed at the other end of said electrical terminals;
the power supply unit comprises two power supply layers and two insulating layers which are used for wrapping the power supply layers respectively;
the power supply unit is connected with an external power supply, and the external power supply supplies power to the external thread interface and the conductive elastic insertion piece respectively through two layers of power supply layers.
3. A reusable igniter for a rocket engine as recited in claim 1, wherein a resilient insulating gasket is disposed at a junction of said male threaded interface and said outer electrode.
4. A reusable igniter for a rocket engine as recited in claim 1, wherein said outer electrode and said inner electrode are fixedly attached by a ceramic insulator;
the ceramic insulating part is positioned in the combustion cavity, and two ends of the ceramic insulating part are respectively embedded into the inner wall of the outer electrode;
the ceramic insulating part is provided with at least one through hole, and the inner electrode penetrates through the through hole and is inserted into the electric control solid propellant.
5. A reusable igniter for a rocket engine as recited in claim 4, wherein said inner electrode comprises at least one electrode post, a conductive disk and a conductive rod;
one end of the electrode column is fixedly connected to one side of the conductive disc, and one end of the conductive rod is fixedly connected to the other side of the conductive disc;
the other end of the electrode column penetrates through the through hole and is inserted into the electric control solid propellant;
the other end of the conducting rod is inserted into the inner ring and is connected with the conductive elastic insertion piece in an inserting mode.
6. A reusable igniter for a rocket engine as recited in claim 5, wherein said electrode post side edges are coated with an insulating layer.
7. A reusable igniter for a rocket engine as recited in claim 5, wherein said number of electrode posts corresponds to said number of through holes; and an assembly gap of 0.1-0.2 mm is arranged between the electrode column and the through hole.
8. A reusable igniter for a rocket engine as recited in claim 7, wherein said assembly gap is sealed by a ceramic-to-metal adhesive glue.
9. A reusable igniter for a rocket engine as recited in claim 1, wherein said outer and inner electrodes are fabricated from a metal or alloy.
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| US9329011B1 (en) * | 2001-02-28 | 2016-05-03 | Orbital Atk, Inc. | High voltage arm/fire device and method |
| CN107620652A (en) * | 2016-10-28 | 2018-01-23 | 湖北航天化学技术研究所 | A kind of multiple-pulse adjustable thrust Solid propeller |
| CN107642435A (en) * | 2016-12-16 | 2018-01-30 | 湖北航天化学技术研究所 | A kind of adjustable thrust, it can repeatedly start automatically controlled solid engine |
| CN108488005A (en) * | 2018-02-13 | 2018-09-04 | 重庆大学 | A kind of multiple-pulse solid propellant rocket of thrust controllable |
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